US8616271B2 - Thermal control device on board a spacecraft - Google Patents
Thermal control device on board a spacecraft Download PDFInfo
- Publication number
- US8616271B2 US8616271B2 US12/037,186 US3718608A US8616271B2 US 8616271 B2 US8616271 B2 US 8616271B2 US 3718608 A US3718608 A US 3718608A US 8616271 B2 US8616271 B2 US 8616271B2
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- US
- United States
- Prior art keywords
- thermal control
- control device
- zone
- refrigerant
- radiating
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
- B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
- B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
- B64G1/503—Radiator panels
Definitions
- the invention relates to a thermal control device on board a satellite or more generally on board a spacecraft.
- satellites comprise a series of pieces of equipment which, when functioning, generate heat that it is necessary to discharge effectively into cold space so that the temperature of this equipment remains within a nominal temperature range.
- the use of heat pipes to transport the heat generated by spacecraft equipment is commonly suggested. Heat pipes transfer thermal energy towards radiators. If the heat pipes form a fluid loop, the radiators can also be deployed thus to increase area of the radiating surfaces after the launch phase to ensure thermal control.
- equipment positioned inside satellites works at temperature ranges such that the discharge temperature of the energy dissipated into space via the radiator structures is limited by these ranges. For a given thermal energy to be removed the required radiating area (and therefore the thermal control mass) is therefore intimately linked to a limiting temperature level.
- the thermal subsystem becomes very large, since it is this which fixes the dimensions of the satellite (surfaces of the satellite walls), unless the use of bulky and heavy dedicated deployable structures is envisaged to increase the area of these radiating surfaces.
- the known solutions for removing the surplus dissipation are essentially the use of capillary fluid loops or mechanically pumped fluid loops linking the interior of the satellite to deployable radiators dedicated to thermal control.
- the latter are bulky and heavy.
- the working temperature of the radiator or radiators (conventional or deployable) is necessarily lower than the maximum temperature acceptable for the equipment to be controlled, which impacts greatly on the dimensions required for these radiators and therefore limits the possibilities for their arrangement on the satellite.
- the present invention proposes the use of a thermal control system of the refrigerating machine type to decouple the equipment whose temperature is to be controlled from the radiators associated with them, that is the temperature of the radiator(s) can be increased as much as is desired.
- the radiators having a direct field of view with cold space, can radiate at very high temperature without impacting on the proper functioning of the equipment so as thus to increase their thermal efficiency and allow a radical reduction in the area of the radiating surfaces dedicated to thermal control in relation to conventional thermal control.
- the device of the invention proposes first to take the thermal dissipation belonging to the satellite or to a part of the satellite (refrigeration energy) using a refrigerant (evaporation zone of the device), then to compress the resultant vapour (thus ensuring circulation of the refrigerant) and thus raising the temperature of the refrigerant.
- the refrigerant in the gas state will condense in the dedicated radiating panels (condensation zone of the device), which discharge, by radiation at high temperature, the total energy into cold space (sum of the refrigeration energy and the compressor's own consumption).
- the pressure of the refrigerant is then reduced (pressure reduction zone of the device) in order to return to the evaporation zone with the appropriate thermodynamic properties.
- the invention is situated in the condensation zone, which comprises the means to vary the area of the heat exchange surface according to the quantity of thermal energy to be discharged into space.
- one subject of the invention is a thermal control device intended to remove the heat generated by heat dissipating equipment on a spacecraft comprising a number of surfaces and including:
- the condensation zone is linked with several radiating panels. These radiating panels are composed of several parts.
- the means for circulating the refrigerant from one part of a radiating panel towards part of another radiating panel are mounted in series.
- the number n of parts per radiating panel is equal to the number n of radiating panels, the n radiating panels therefore being connected in series by n ⁇ 1 means of circulation, the n parts being passed through by the refrigerant having an identical discharge area.
- the branches consist of tubes with grooved surfaces.
- the condensation zone comprises a system of automatic valves allowing all or part of the surface of the radiating panel to be used to remove heat, the refrigerant then circulating in all or part of the said branches.
- the evaporation zone furthermore comprises heating means allowing centralized heating.
- heating means allowing centralized heating.
- the thermal dissipation of the satellite or of the equipment concerned can be replaced by heating if the equipment dissipates too little or no longer dissipates.
- the opportunity should be noted here of being able to heat centrally, that is to have a set of heaters more or less grouped together and located somewhere on the means for circulating the refrigerant downstream of the condenser and upstream of the compressor.
- These heating zones are nothing but further evaporation zones that are used if needed. This simplifies considerably the design of the heating lines.
- the evaporation zone comprises one or more pieces of equipment controlled at a single temperature level or at several different temperature levels.
- the compression zone comprises several compression stages, the number of stages being equal to the number of temperature levels of the evaporator to be controlled.
- the compression zone comprises at least one magnetic-bearing centrifugal compressor.
- the device comprises a bypass system between the compression zone and the condensation zone, allowing the temperature of the refrigerant to be adjusted.
- Another subject of the invention is a spacecraft including a thermal control device according to the invention.
- this is a telecommunications spacecraft with faces commonly called North and South, characterized in that it comprises external radiating panels, fixed to the North and South faces, equipped with the condensation zone of the thermal control device, the said radiating panels being conductively and radiatively decoupled from these North and South faces.
- the spacecraft comprises evaporation, compression and pressure reduction zones inside the spacecraft.
- it comprises a communication module and a service module, the external radiating panels being situated on the communication module.
- FIG. 1 is a scheme of the various condensation, pressure reduction, evaporation and compression zones used in a device of the invention
- FIG. 2 illustrates an example of a device according to the invention
- FIG. 3 illustrates an example of the external architecture used in a telecommunications satellite that integrates a device of the invention.
- the thermal control device of the invention comprises various components designed to take on the diverse environmental constraints and diverse operating constraints of the satellite or of the equipment controlled.
- the device of the invention is illustrated schematically in FIG. 1 . It comprises an evaporation zone Z 1 , a compression zone Z 2 , a condensation zone Z 3 and a pressure reduction zone Z 4 , as well as means for circulating a refrigerant.
- the refrigerant condenses in the dedicated radiating panels (condensation zone Z 3 of the device), which discharge, by radiation at high temperature, the total energy into cold space.
- These panels are thermally, conductively and radiatively, decoupled from the support structures of the equipment, which allows the temperature of the radiators to be increased significantly without impacting on the temperature of the satellite's equipment and therefore on its proper functioning.
- the pressure of the refrigerant is then reduced (pressure reduction zone Z 4 of the device) in order to return to the evaporation zone with the appropriate thermodynamic properties.
- the temperatures of the one or more pieces of equipment and of the radiating panel(s) can be chosen to be as low or as high as desired. If it is necessary to keep various parts of the satellite at different temperature levels, it is advantageous to use a multistage compression concept which, notably, allows the device output to be increased.
- the radiators linked with the condensation zone can be situated anywhere on the exterior of the satellite provided that they do not disturb the proper running of the mission (notably, field of view with external appendages) and that their interaction with the propulsion subsystem is not critical (pollution of the radiating surfaces and therefore loss of efficiency of the latter over the lifetime of the satellite).
- the possibility of discharging the thermal dissipation of the satellite at high temperature also allows the use of coatings not optimized for radiating panels (for example, white paint).
- coatings not optimized for radiating panels for example, white paint.
- the incident solar flux absorbed per unit area can become of second order compared with the infrared flux discharged by the panels if the radiation temperature of the latter is correctly chosen.
- the use of mirror coatings is then no longer necessary. The manufacturing cost and the mass of the radiators can thus be reduced.
- the condensation zone Z 3 comprising several branches in the means for circulating the refrigerant, will be described in a more detailed manner in an exemplary embodiment.
- the type of circulation suggested makes the system robust and guarantees thermal control throughout the life of the satellite, that is to say for very varied environmental conditions and very variable cases of thermal loading (refrigeration energy).
- the system of the invention assures thermal control for a large number of working modes of the satellite or of the thermally controlled equipment (low and high thermal loading, worst hot and worst cold environments) from the launch phase until the end of its life. Thanks to the device of the invention it is possible to double the total heat discharge capacity of a telecommunications satellite and therefore, for a given platform size, to be able to accept missions twice as energetic as at present without necessarily changing the scale of the platform.
- FIG. 2 reveals in more detail all the various specific zones that provide the thermal system with a large capacity with regard to the loading of the thermal control through the life of the satellite.
- the refrigerant circulates within the evaporation zone inside tubes with standard geometrical properties or those that are to be locally designed.
- the tubes can, advantageously, be grooved if it is desired to increase the heat exchange coefficients (in relation to a smooth-tube configuration).
- the design of an optimal series/parallel hydraulic scheme depends on system constraints (energy to be transported, temperature ranges, arrangement of the equipment to be controlled), but also on the refrigerant chosen.
- FIG. 2 illustrates a configuration with two evaporation zones Z 11 and Z 12 , each linked to respective dissipating elements 11 and 12 .
- the compression zone can, advantageously, comprise several compression stages.
- the multistaging of the compression zone allows the satellite or equipment to be regulated at different temperature levels. These levels depend on, among other things, the type of equipment considered or the zone of the satellite concerned. This possibility allows the compressor's electrical consumption to be optimized.
- FIG. 2 thus illustrates the system for a two-stage configuration comprising two compression zones Z 21 and Z 22 . It may be noted that it is the compression zone which, through its mechanical action on the refrigerant, ensures circulation of the latter through the whole of the system.
- magnetic-bearing centrifugal compressor technology can be adopted (little vibration, no need for lubrication, little friction, low electrical consumption, low bulk) because it combines well with the constraints of space, specifically with those in geostationary orbit, and with the strong constraint of long life.
- bypass radiator solution using a bypass B-P allowing the temperature of the vapour exiting the final compression stage to be raised in such a way as to obtain a fairly high condensation temperature without putting too much stress on the compressor, and this so as to be able to overcome hot radiator environments.
- this bypass regulates the quantity of refrigerant leaving the compressor that is taken back into the inlet of the latter. This possibility is particularly interesting when the refrigeration energy to be transported must remain low or moderate (system constraint).
- the solar generators are able to face, according to the positioning in space of the satellite, a hot environment (incident solar flux).
- bypass solution allows the system to ensure the thermal control of several pieces of equipment of the satellite's payload in operation and in contact with Earth (limited electric power budget in this phase).
- the refrigerant circulates within the condensation zone of the radiators inside tubes with standard dimensional properties or those that have to be locally designed.
- the optimal series/parallel hydraulic scheme (and hence the number of branches) within the radiators depends on system constraints (energy to be transported, type of radiator structure chosen, etc.), but also on the refrigerant chosen.
- the hydraulic scheme suggested is specific for two reasons:
- the pressure reduction zone may include thermostatic pressure-reducing valves.
- the pressure-reducing valves constituting this pressure reduction zone may be arranged in series or in parallel with respect to the evaporation zone if there is multistage compression.
- the thermal dissipation of the satellite or of the equipment concerned can be replaced by heating.
- the opportunity must be noted here of being able to heat centrally, that is to have a set of heaters more or less grouped together and located somewhere on the tubing downstream of the condenser and upstream of the compressor.
- These heating zones X 11 and X 12 are nothing but new evaporation zones that are used if needed according to a regulation principle.
- the device of the invention both allows the problem of the dissipated energy/consumed energy ratio, which is tending to increase in view of future telecommunications satellite missions, to be dealt with and provides possibilities for regulating the compressor and a number of active condenser lines; this allows variable conductance operation and a large reduction in the need for and the size of heating lines. It allows the payload to be controlled in several temperature ranges (system constraint) due to the multistage compression principle for minimizing the electrical consumption necessary for compression.
- the device of the invention can specifically be used in a very advantageous manner for the thermal control of a telecommunications payload.
- the thermal dissipation of these payloads is removed into space via the North and South support panels of the equipment, which on their external face therefore also serve as radiators.
- This system of thermal control it becomes possible to remove the payload heat by using radiating plates fixed externally to the North and South panels, at best parallel to and conductively and radiatively decoupled from the latter.
- the external surface of the North and South walls is then no longer used for radiating purposes, but is covered with an insulating coating to preserve the equipment inside from the high temperature levels of the radiators.
- FIG. 3 schematically illustrates the external radiator architecture as proposed for this example of a thermal control solution for telecommunications satellites.
- the radiating plates P N and P S are fixed externally to the North and South faces of the satellite and parallel to the latter. These radiating plates are best conductively and radiatively decoupled from the satellite and comprise the condensation zone of the thermal dissipation discharge device.
- the North, South, East and West faces of the satellite's communication module Mc are covered with a conventional multilayer coating called “MLI” and referred to as MLI (Multi-Layer Insulation), in contrast to structures of the prior art which necessitated coating the North and South faces with a mirror coating.
- MLI Multi-Layer Insulation
- These radiating plates are positioned opposite the North and South faces of the satellite at the communication module, the point where thermal problems are greatest.
- conventional thermal control solutions based on heat pipes and mirror coatings for the radiators m r (on the North and South faces) may still be used as the thermal problems are of lesser proportion.
- the invention is nonetheless extendable to the service module Ms if necessary.
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- Engineering & Computer Science (AREA)
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- Life Sciences & Earth Sciences (AREA)
- Environmental & Geological Engineering (AREA)
- Environmental Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toxicology (AREA)
- Biodiversity & Conservation Biology (AREA)
- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
- Cooling Or The Like Of Electrical Apparatus (AREA)
- Other Air-Conditioning Systems (AREA)
- Laminated Bodies (AREA)
- Thermotherapy And Cooling Therapy Devices (AREA)
- Chemical And Physical Treatments For Wood And The Like (AREA)
- Cylinder Crankcases Of Internal Combustion Engines (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0753500A FR2912995B1 (fr) | 2007-02-26 | 2007-02-26 | Dispositif de controle thermique embarque a bord d'un engin spatial |
FR0753500 | 2007-02-26 |
Publications (2)
Publication Number | Publication Date |
---|---|
US20080217483A1 US20080217483A1 (en) | 2008-09-11 |
US8616271B2 true US8616271B2 (en) | 2013-12-31 |
Family
ID=38434815
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/037,186 Active 2032-05-29 US8616271B2 (en) | 2007-02-26 | 2008-02-26 | Thermal control device on board a spacecraft |
Country Status (8)
Country | Link |
---|---|
US (1) | US8616271B2 (de) |
EP (1) | EP1961659B1 (de) |
JP (1) | JP5282283B2 (de) |
CN (1) | CN101270930B (de) |
AT (1) | ATE465086T1 (de) |
DE (1) | DE602008001001D1 (de) |
ES (1) | ES2341057T3 (de) |
FR (1) | FR2912995B1 (de) |
Cited By (6)
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US9352856B1 (en) * | 2013-12-04 | 2016-05-31 | Space Systems/Loral, Llc | Axially grooved crossing heat pipes |
US9902507B2 (en) * | 2015-01-27 | 2018-02-27 | Airbus Defence And Space Sas | Artificial satellite and method for filling a tank of propellent gas of said artificial satellite |
US10118717B2 (en) * | 2015-06-02 | 2018-11-06 | Airbus Defence And Space Sas | Artificial Satellite |
US10155597B2 (en) | 2015-08-10 | 2018-12-18 | Airbus Defence And Space Sas | Artificial satellite |
US10780998B1 (en) | 2017-03-22 | 2020-09-22 | Space Systems/Loral, Llc | Spacecraft design with multiple thermal zones |
US11814195B1 (en) * | 2019-08-26 | 2023-11-14 | United States Of America As Represented By The Administrator Of Nasa | Silicon oxide coated aluminized Kapton radiator coating for nano-satellite thermal management |
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JP5496212B2 (ja) * | 2008-10-02 | 2014-05-21 | イベリカ デル エスパシオ、ソシエダッド アノニマ | 宇宙船のための、熱源からの熱負荷を制御する熱モジュール、及び宇宙船モジュール式熱プラットホーム |
FR2942774B1 (fr) * | 2009-03-06 | 2011-05-06 | Thales Sa | Dispositif de controle thermique pour un engin spatial |
CN101508349B (zh) * | 2009-03-17 | 2010-08-25 | 北京航空航天大学 | 一种适用于纳卫星热控系统的流体回路控制装置 |
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US9091489B2 (en) | 2010-05-14 | 2015-07-28 | Paragon Space Development Corporation | Radiator systems |
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JP5003829B2 (ja) * | 2011-01-19 | 2012-08-15 | ダイキン工業株式会社 | 空気調和機 |
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CN104504176B (zh) * | 2014-12-02 | 2016-05-04 | 北京空间飞行器总体设计部 | 重力驱动两相流体回路中储液器和工质充装量的匹配方法 |
FR3030458B1 (fr) * | 2014-12-18 | 2017-01-27 | Airbus Defence & Space Sas | Engin spatial |
US10583940B2 (en) | 2015-03-03 | 2020-03-10 | York Space Systems LLC | Pressurized payload compartment and mission agnostic space vehicle including the same |
US9908643B2 (en) * | 2015-08-05 | 2018-03-06 | Worldvu Satellites Limited | Passive thermal system providing an embedded interface for heat pipes |
CN106828985B (zh) * | 2016-12-29 | 2019-01-15 | 重庆大学 | 一种燃料汽化吸热运载火箭冷却系统 |
US10696429B2 (en) * | 2017-02-03 | 2020-06-30 | The Boeing Company | Dual condenser loop heat pipe for satellites with sun-normal radiators |
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CN111152940B (zh) * | 2020-01-02 | 2021-05-18 | 中国科学院空间应用工程与技术中心 | 一种辅助传热机构、舱外载荷和空间站 |
US11320216B2 (en) | 2020-01-29 | 2022-05-03 | Hamilton Sundstrand Corporation | Insert for evaporator header |
US11808528B2 (en) | 2020-02-03 | 2023-11-07 | Hamilton Sundstrand Corporation | Evaporator with grooved channels and orifice inserts |
US11512908B2 (en) | 2020-02-03 | 2022-11-29 | Hamilton Sundstrand Corporation | Evaporator with grooved channels |
CN112231837B (zh) * | 2020-10-22 | 2022-11-29 | 上海卫星工程研究所 | 基于航天器大面积热控方案的分布式热控设计系统 |
CN113212811B (zh) * | 2021-06-24 | 2023-03-24 | 中国科学院微小卫星创新研究院 | 兼容动态磁补偿的热控制系统 |
CN114455106A (zh) * | 2022-02-21 | 2022-05-10 | 航天科工空间工程发展有限公司 | 一种热控结构及包括该热控结构的卫星 |
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- 2008-02-26 DE DE602008001001T patent/DE602008001001D1/de active Active
- 2008-02-26 EP EP08102023A patent/EP1961659B1/de active Active
- 2008-02-26 ES ES08102023T patent/ES2341057T3/es active Active
- 2008-02-26 US US12/037,186 patent/US8616271B2/en active Active
- 2008-02-26 CN CN2008100951355A patent/CN101270930B/zh not_active Expired - Fee Related
- 2008-02-26 AT AT08102023T patent/ATE465086T1/de not_active IP Right Cessation
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US11814195B1 (en) * | 2019-08-26 | 2023-11-14 | United States Of America As Represented By The Administrator Of Nasa | Silicon oxide coated aluminized Kapton radiator coating for nano-satellite thermal management |
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EP1961659B1 (de) | 2010-04-21 |
US20080217483A1 (en) | 2008-09-11 |
ES2341057T3 (es) | 2010-06-14 |
FR2912995B1 (fr) | 2009-05-22 |
CN101270930B (zh) | 2012-06-27 |
CN101270930A (zh) | 2008-09-24 |
JP5282283B2 (ja) | 2013-09-04 |
EP1961659A1 (de) | 2008-08-27 |
JP2008222210A (ja) | 2008-09-25 |
DE602008001001D1 (de) | 2010-06-02 |
ATE465086T1 (de) | 2010-05-15 |
FR2912995A1 (fr) | 2008-08-29 |
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